Design and manufacturing of a quad tilt rotor unmanned air vehicle

Download

index.pdf

Date

2014

Author

Kahvecioğlu, Ahmet Caner

Metadata

Show full item record

Item Usage Stats

374
views

164
downloads

This thesis presents the design and manufacturing process of a mini class quad tilt rotor unmanned air vehicle (UAV). An optimal design procedure is conducted to satisfy a set of pre-determined requirements, which ensure a competitive aircraft platform performing primarily intelligence, surveillance and reconnaissance missions in UAV market. The aircraft has four electric motors with tilting capability in one axis, which gives it the opportunity to combine the vertical take-off and landing capabilities with long endurance and good maximum cruise speed. In addition, as a result of the physical concept and the modular design of the aircraft, wing and tail parts of the aircraft can be demounted, so that the aircraft is converted to a highly maneuverable quad-rotor, which has a longer hovering time capacity than the full aircraft and is more appropriate for missions requiring stealth. The thesis includes the construction of a mathematical model which calculates all of the weight estimation parameters and geometrical and performance outputs; generation of different design cases using this mathematical model and the procedure for an optimal design choice; construction of the outer geometry and inner structure vi of the aircraft; manufacturing of the molds and the composite skins of the aircraft; and assemblage of the aircraft. Outputs of the mathematical model are compared with computational fluid dynamics (CFD) solutions to justify the analytical calculations. Besides, static loading tests are conducted to examine the structural design of the airframe. The main objective of the study is to give an idea about the feasibility of developing a new concept of a mini class UAV.

Subject Keywords

Quadrotor helicopters., Vehicles, Remotely piloted., Rotors (Helicopters), Quadrotor helicopters

URI

http://etd.lib.metu.edu.tr/upload/12618110/index.pdf
https://hdl.handle.net/11511/24091

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Modeling and experimental identification of quadrotor aerodynamics Kaya, D. Derya; Kutay, Ali Türker; Department of Aerospace Engineering (2014) The aim of this study is to obtain mathematical models for aerodynamic forces and moments of rotors of a quadrotor helicopter, and estimate their parameters through wind tunnel tests for hover, vertical climb, and forward flight conditions. The main factors which determine the movement of a quadrotor UAV are the aerodynamic forces and moments in three axes created by four rotors of the vehicle. Hence, accurate calculation of rotor forces and moments in varying flight conditions are essential to establish a ...
Design and Manufacturing of a High Speed Jet Powered UAV Ozyetis, Ender; Alemdaroglu, Nafiz (2014-05-30) This paper presents the design and manufacturing of a high speed jet powered UAV which is capable of flying at M=0.5. Flight time of the UAV is 30 minutes at 1700 m above sea level. Aerodynamic and structural design of the UAV is conducted for 6g sustained and 9g instantaneous loads. Low aspect ratio blended wing-body design is decided due to low drag and high maneuverability. Structure of the UAV consists of the composite parts such as frames and skin and mechanical parts such as landing gears which are fr...
Design and Analysis of an Unmanned Aerial Vehicle Hybrid Trailing Edge Control Surface Having Camber and Decamber Capabilities Topaç, Ömer Tanay; Taşdemir, Burcu; Gürses, Ercan; Çöker, Demirkan (2015-09-12) This paper presents the design and analyses of an unmanned aerial vehicle hybrid trailing edge control surface having camber and decamber capabilities. Initially, a brief introductory information were given about morphing concepts. Then, the structural design and analyses in in-vacuo condition are presented. The aerodynamic loadings were calculated at the morphed configurations, and these loads were transferred to the structural mesh in order to assess the design capability under the aerodynamic loading. It...
Aerodynamic design and control of tandem wing unmanned aerial vehicle Kaya, Taşkın; Özgen, Serkan; Department of Aerospace Engineering (2019) This thesis presents an approach towards the design methodology of electrical propulsion, tandem wing unmanned aerial vehicle. Due to its possible rewarding features, tandem wing design is investigated as the main subject of this study. The stability and control characteristics of tandem wing aircraft are critical since the interference between the two wings may result in nonlinear aerodynamic characteristics for varying angles of attack. Thus, the design of the controller system requires careful handling, ...
Optimal Design of a Miniature Quad Tilt Rotor UAV Kahvecioglu, Ahmet Caner; Alemdaroglu, Nafiz (2015-06-12) This paper describes the design procedure of a convertible miniature (mini and micro) quad tilt rotor unmanned air vehicle (UAV), which has about 2 meters of wing span, one hour of mission time and 5 kilograms of total weight. The aircraft is driven by four brushless direct current motors, and the structure of it completely made of composite materials. When the wing and tail of the aircraft are dismounted, it operates as a quad- rotor with tilting rotors. The aircraft is planned to carry a gimbal camera wei...

Citation Formats

A. C. Kahvecioğlu, “Design and manufacturing of a quad tilt rotor unmanned air vehicle,” M.S. - Master of Science, Middle East Technical University, 2014.